EP0731331A2 - Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie - Google Patents

Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie Download PDF

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Publication number
EP0731331A2
EP0731331A2 EP96102429A EP96102429A EP0731331A2 EP 0731331 A2 EP0731331 A2 EP 0731331A2 EP 96102429 A EP96102429 A EP 96102429A EP 96102429 A EP96102429 A EP 96102429A EP 0731331 A2 EP0731331 A2 EP 0731331A2
Authority
EP
European Patent Office
Prior art keywords
missile
support body
launch tube
ready
electrical contact
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP96102429A
Other languages
German (de)
English (en)
Other versions
EP0731331A3 (fr
EP0731331B1 (fr
Inventor
Heinrich Gertz
Wolfram Vaihinger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Wegmann and Co GmbH
Original Assignee
Wegmann and Co GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Wegmann and Co GmbH filed Critical Wegmann and Co GmbH
Publication of EP0731331A2 publication Critical patent/EP0731331A2/fr
Publication of EP0731331A3 publication Critical patent/EP0731331A3/fr
Application granted granted Critical
Publication of EP0731331B1 publication Critical patent/EP0731331B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms
    • F41A19/69—Electric contacts or switches peculiar thereto
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor

Definitions

  • the invention relates to a launching device for self-propelled missiles, in particular artillery rockets, with the features from the preamble of patent claim 1.
  • the invention has for its object to provide a launcher of the type described in the preamble of claim 1, in which, on the one hand, the electrical signal transmission to the missile is carried out so that no tearing of cable connections has to be accepted and, on the other hand, opens up possibilities to to prevent the support body from coming into contact with parts of the missile after leaving the launch tube.
  • a basic idea of the invention is to design the support body so that the electrical energy transmission takes place under the force of compression springs contact pins which are in the ready-to-fire state against mating contacts on the inside of the launch tube and each are also electrically connected to contact pins which are also under the force of compression springs and which bear against electrical mating contacts on the outside of the missile.
  • the force of the compression springs used only serves to generate the necessary contact pressure on the electrical contact pins.
  • a similar design principle also prevents the support bodies from coming into contact with parts of the missile after leaving the launch tube.
  • the support bodies are designed so that they receive a strong impulse transversely to the launch direction when they leave the launch tube and are thus thrown outwards so that they are at a sufficient distance from the missile when the tail unit has left the launch tube. This momentum is generated by spring-loaded plungers, which push the support body away from the missile.
  • the force of the compression springs used for this is much greater than the force of the compression springs which generate the contact pressure on the electrical contact pins.
  • One or more launch tubes A are arranged on a base frame G. 1 is within the launch tube A a ready-to-fire missile F, which is supported at its rear end via a tail unit L on the inner wall of the launch tube A, while in its front region it is arranged over a total of four at equal angular intervals on its circumference Support body S1, S2 supported on the inner wall of the launch tube A.
  • electrical lines Z which are connected to electrical contacts GK1 arranged in the inner wall of the launch tube 8, are supplied with electrical signals which, in a manner explained below, pass through the supporting bodies S1 and S2 to electrical contacts GK2 which are located in the outer surface of the missile F.
  • the signals are supplied to the rocket propulsion in a manner known per se and the missile F starts to move in the launch direction.
  • 2 shows a moment shortly before the missile F completely exits the launch tube A.
  • the missile F is still supported within the launch tube A via the tail unit L, while the support bodies S1 and S2 - and two further support bodies, not shown - are made of are led out of the launch tube A and, due to their construction, which is explained in more detail below, receive a strong impulse in the arrow direction Q, that is to say the direction transverse to the launch direction.
  • Fig. 3 shows that due to this pulse after the missile F has completely emerged from the launch tube 8, the support bodies S1 and S2 have moved so far away from the missile F that there is no longer a collision with the tail unit L.
  • the support body S1 has an upper part 1 and a lower part 2, which are detachably connected to one another via a screw connection 3.
  • An interior space 13 is delimited within the support body by the upper and lower part.
  • the upper side of the upper part 1 is adapted at least in partial areas 1.1 to the inner surface of the launch tube, while the lower side 2.1 of the lower part 2 is adapted to the outer shape of the missile F.
  • the distance between the underside 2.1 of the lower part 2 and the upper side 1.1 of the upper part 1 is shown as a radius section R, which determines the difference in caliber between the missile F and the launch tube A.
  • guide grooves 1.3 are further arranged, through which support straps are drawn in a manner not shown and known, with which the supporting bodies are attached to the missile before it is inserted into the launch tube. After the missile has been inserted into the launch tube, after the support bodies are supported on the inner wall of the launch tube, these bands are pulled out again.
  • two plungers 4 are arranged, which are guided at their rear end on guide pieces 2.2 with guide surfaces 2.3 in the direction of the underside 2.1.
  • Strong helical compression springs 5 are supported on the guide pieces 2.2, each of which rests with its other end on a collar 4.2 of the tappet 4 and thus exert a force effect in such a way that the outer end 4.1 of the plunger 4 in the non-installed state of the support body shown in the figures protrudes from openings from the underside 2.1 of the lower part 2 by a predetermined amount.
  • the front ends 4.1 of the plunger 4 are guided on guide surfaces 2.4 in the lower part 2.
  • the outer ends 4.1 of the plunger 4 sit on the surface of the missile and are pressed fully into the lower part 2 against the action of the compression springs 5 in the ready-to-fire state.
  • the support body is brought out of the launch tube during firing, the support body is pressed off by the missile with a strong impulse due to the force of the compression springs 5 via the plunger 4.
  • the support body attached to the missile is guided on the missile via a guide part 9 which is under the action of a compression spring 10 and which extends in the longitudinal direction and engages with its outer part 9.1 in a corresponding groove on the surface of the missile (see FIGS. 5 and 7).
  • the lower and upper electrical contact pins are insulated from the body of the lower part and the upper part in a manner not shown, for example in such a way that they are made of plastic with an electrically conductive core.
  • Each of the lower contact pins 7 is connected to an associated upper contact pin 6 via a spiral conductor 8, which performs both the function of an electrical conductor and the function of a compression spring, against the action of which the outer ends 6.1 and 7.1 of the contact pins can be pressed back.
  • the outer ends 7.1 and 6.1 of the contact pins rest against corresponding counter-contacts GK2 and GK1 (see FIG. 1) of the missile or the launch tube, the required contact pressure being generated by the spiral conductors 8.
  • the pressure generated by the helical conductor 8 acting as compression springs 8 is significantly lower than the pressure generated by the helical compression springs 5 for pushing off the support bodies after the launch.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Elimination Of Static Electricity (AREA)
EP96102429A 1995-03-07 1996-02-17 Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie Expired - Lifetime EP0731331B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19508008 1995-03-07
DE19508008A DE19508008A1 (de) 1995-03-07 1995-03-07 Abschußvorrichtung für selbstangetriebene Flugkörper, insbesondere Artillerieraketen

Publications (3)

Publication Number Publication Date
EP0731331A2 true EP0731331A2 (fr) 1996-09-11
EP0731331A3 EP0731331A3 (fr) 1996-11-27
EP0731331B1 EP0731331B1 (fr) 1998-04-15

Family

ID=7755900

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96102429A Expired - Lifetime EP0731331B1 (fr) 1995-03-07 1996-02-17 Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie

Country Status (2)

Country Link
EP (1) EP0731331B1 (fr)
DE (2) DE19508008A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009121467A1 (fr) * 2008-04-03 2009-10-08 Rheinmetall Waffe Munition Gmbh Projectile à sabot
JP2011242124A (ja) * 2010-05-13 2011-12-01 Oto Melara Spa 携帯用拳銃の爆発雷管にデータを送信するためのシステム
WO2015082701A1 (fr) * 2013-12-06 2015-06-11 Rheinmetall Waffe Munition Gmbh Dispositif de contact modulaire, permettant en particulier la mise en contact électrique d'une arme dans laquelle se trouve une munition
FR3099393A1 (fr) 2019-08-01 2021-02-05 Psa Automobiles Sa Presse d’emboutissage avec lancement de galet

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014016340B3 (de) * 2014-11-05 2015-08-20 Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr Programmiergerät zum Programmieren einer programmierbaren Artilleriemunition
DE102021000884B4 (de) 2021-02-19 2023-07-27 Mbda Deutschland Gmbh Nutzlastträger sowie dichtungs-kit und verbindungsverfahren zum abdichten eines zwischenraumes
CN113357963B (zh) * 2021-06-15 2023-03-07 湖北航天技术研究院总体设计所 一种用于控制发射装置辅助支腿下放的方法和系统

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3120784A (en) * 1962-02-19 1964-02-11 William M Magers Booster contactor
US3610095A (en) * 1967-06-29 1971-10-05 Us Army Rocket means for driving a free punch
US4455916A (en) * 1982-02-22 1984-06-26 The United States Of America As Represented By The Secretary Of The Navy Armament shorting arrangement
US4638739A (en) * 1986-02-14 1987-01-27 The United States Of America As Represented By The Secretary Of The Army Sabot for an electromagnetically-accelerated, unguided hypervelocity penetrator
USH405H (en) * 1987-08-24 1988-01-05 The United States Of America As Represented By The Secretary Of The Army Rocket/launcher interface

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE310009C (fr) *
US2998780A (en) * 1956-05-28 1961-09-05 William B Anspacher High velocity, fin stabilized projectile, rifled barrel gun system
IL37041A (en) * 1971-06-14 1976-02-29 State Of Il Ministry Of Def Forward sabot for sub-calibre projectile with delayed detachment
DE3211011A1 (de) * 1982-03-25 1983-09-29 Dynamit Nobel Ag, 5210 Troisdorf Uebungsrakete
DE3414911A1 (de) * 1984-04-19 1985-10-24 Dynamit Nobel Ag, 5210 Troisdorf Flugkoerper, insbesondere ballistische rakete
DE3939037C2 (de) * 1989-11-25 1994-01-27 Diehl Gmbh & Co Rohrwaffenförmige Starteinrichtung für Unterwasser-Projektil

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3120784A (en) * 1962-02-19 1964-02-11 William M Magers Booster contactor
US3610095A (en) * 1967-06-29 1971-10-05 Us Army Rocket means for driving a free punch
US4455916A (en) * 1982-02-22 1984-06-26 The United States Of America As Represented By The Secretary Of The Navy Armament shorting arrangement
US4638739A (en) * 1986-02-14 1987-01-27 The United States Of America As Represented By The Secretary Of The Army Sabot for an electromagnetically-accelerated, unguided hypervelocity penetrator
USH405H (en) * 1987-08-24 1988-01-05 The United States Of America As Represented By The Secretary Of The Army Rocket/launcher interface

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
NAVY TECHNICAL DISCLOSURE BULLETIN, Bd. 8, Nr. 3, M{rz 1983, WASHINGTON (USA), Seiten 55-57, XP002014112 D. EDMONDS: "Missile interface connector" *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009121467A1 (fr) * 2008-04-03 2009-10-08 Rheinmetall Waffe Munition Gmbh Projectile à sabot
JP2011242124A (ja) * 2010-05-13 2011-12-01 Oto Melara Spa 携帯用拳銃の爆発雷管にデータを送信するためのシステム
WO2015082701A1 (fr) * 2013-12-06 2015-06-11 Rheinmetall Waffe Munition Gmbh Dispositif de contact modulaire, permettant en particulier la mise en contact électrique d'une arme dans laquelle se trouve une munition
FR3099393A1 (fr) 2019-08-01 2021-02-05 Psa Automobiles Sa Presse d’emboutissage avec lancement de galet

Also Published As

Publication number Publication date
EP0731331A3 (fr) 1996-11-27
DE19508008A1 (de) 1996-09-12
DE59600152D1 (de) 1998-05-20
EP0731331B1 (fr) 1998-04-15

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